Fault Detection and Isolation for Deep Space Satellites

Williamson, Walton R.; Speyer, Jason L.; Dang, Vu T.; Sharp, James

doi:10.2514/1.41319

Cited by 38 publications

(10 citation statements)

References 4 publications

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“…It is easily concluded from (19) that the spacecraft attitude is ultimately uniformed bounded. Moreover, using (4), one has F 1 .x 2 / 6 16 .1C T / 2 kF k 6 8.…”

Section: Proofmentioning

confidence: 99%

Active fault‐tolerant attitude control for flexible spacecraft with loss of actuator effectiveness

Xiao

Friswell

2012

Adaptive Control & Signal

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A theoretical framework for active fault-tolerant attitude stabilization control is developed and applied to flexible spacecraft. The proposed scheme solves a difficult problem of fault-tolerant controller design in the presence of severe partial loss of actuator effectiveness faults and external disturbances. This is accomplished by developing an observer-based fault detection and diagnosis mechanism to reconstruct the actuator faults. Accordingly, a backstepping-based fault-tolerant control law is reconfigured using the reconstructed fault information. It is shown that the proposed design approach guarantees that all of the signals of the closedloop system are uniformly ultimately bounded. The closed-loop performance of the proposed control strategy is evaluated extensively through numerical simulations. 926 B. XIAO, Q. HU AND M. I. FRISWELLTo achieve fault tolerance capability with satisfactory performance, a number of new fault-tolerant control (FTC) approaches have been proposed in the literature; good overviews and extensive bibliographic references have been provided in [2][3][4][5]. As spacecraft attitude dynamics is modeled with inherent nonlinearity, external disturbances, and system uncertainties, such intrinsic complexity makes the straightforward application of many cited FTC schemes in [2][3][4][5] and the references therein infeasible for spacecraft attitude systems. Therefore, FTC design for spacecraft system applications is still an open problem for further research. At present, there are two approaches to synthesize controllers that are tolerant to system faults, known as passive FTC (PFTC), and active FTC (AFTC). PFTC is designed and implemented using a fixed controller without any fault detection and diagnosis (FDD) mechanism, as suggested in [6][7][8][9][10][11].Passive FTC has the drawback that it is only reliable for the class of faults expected in the design process, and achieving robustness to certain faults is only possible at the expense of decreased nominal performance. In contrast to the PFTC, the AFTC can react to fault events and relies on the availability of an FDD mechanism that gives, in real-time, information about the nature and the intensity of the fault. This information is then used by a control configuration module to adjust the control effort online in such a way to maintain stability and to optimize the performance of the faulty system. Hence, the work presented in this study falls into the AFTC category. Recently, FDD has become an ever increasingly important area of research activity, and many investigations on FDD have been conducted for linear and nonlinear systems [12][13][14]. Wang and Lum [15] developed an unknown input observer to detect and isolate actuator faults in aircraft by using an adaptive technique. Curry and Collins [16] proposed an alternative solution to the FDD problem with the application of robust l 1 estimation.Unfortunately, most of the preceding FDD research is only feasible and applicable for linear systems. The intrinsic complexities of spacecr...

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“…It is easily concluded from (19) that the spacecraft attitude is ultimately uniformed bounded. Moreover, using (4), one has F 1 .x 2 / 6 16 .1C T / 2 kF k 6 8.…”

Section: Proofmentioning

confidence: 99%

Active fault‐tolerant attitude control for flexible spacecraft with loss of actuator effectiveness

Xiao

Friswell

2012

Adaptive Control & Signal

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“…Beside gyroscopes, attitude sensors such as star trackers [5], sun sensors and earth sensors [6,7,8] or redundant gyroscopes [9] can lead to FDI solutions. Most of these studies utilize different linear and nonlinear filtering approaches.…”

Section: Introductionmentioning

confidence: 99%

Fault detection and isolation of satellite gyroscopes using relative positions in formation flying

Shakouri

Assadian

2018

Aerospace Science and Technology

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A fault detection and isolation method for satellite rate gyros is proposed based on using the satellite-to-satellite measurements such as relative position beside orbit parameters of the primary satellite. By finding a constant of motion, it is shown that the dynamic states in a relative motion are restricted in such a way that the angular velocity vector of primary satellite lies on a quadratic surface. This constant of motion is then used to detect the gyroscope faults and estimate the corresponding scale factor or bias values of the rate gyros of the primary satellite. The proposed algorithm works even in time variant fault situations as well, and does not impose any additional subsystems to formation flying satellites. Monte-Carlo simulations are used to ensure that the algorithm retains its performance in the presence of uncertainties. In presence of only measurement noise, the isolation process performs well by selecting a proper threshold. However, the isolation performance degrades as the scale factor approaches unity or bias approaches zero. Finally, the effect of orbital perturbations on isolation process is investigated by including the effect of zonal harmonics as well as drag and without loss of generality, it is shown that the perturbation effects are negligible.

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“…The vehicle considered is a deep-space satellite with 12 thrusters (organized in 4 sets), similar to the one presented in [12]. The state of the satellite is described in Eq.…”

Section: Satellite Dynamicsmentioning

confidence: 99%

“…Different model-based methods have been studied for satellite models: parity space [10], neural-network [8], parameter estimation techniques [4], observerbased techniques [1], bank of Kalman filters [12] and techniques based on unknown input observer (UIO) [6].…”

Section: Introductionmentioning

confidence: 99%

A Multiple-Observer Scheme for Fault Detection, Isolation and Recovery of Satellite Thrusters

Abauzit

Marzat

2013

Advances in Aerospace Guidance, Navigation and Control

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The method proposed in this paper aims at automatically detecting, isolating and identifying faults on actuators of a satellite model and also aims at automatically reconfiguring the reference input once the fault has been isolated. The method uses two sliding mode observers to detect and reconstruct the fault. A cusum test on the output of the detection observer triggers a bank of Unknown Input Observers in order to isolate the faulty actuator. The reference input is automatically reconfigured in order to pre-compensate the fault, which makes the satellite capable of fulfilling its mission with the desired performances and good precision. Monte Carlo analysis, based on performance criteria, is carried out to assess the performance of the strategy. The combination of these different types of filters might provide better detection, isolation and identification capabilities than a single filter that would be forced to achieve a trade-off between fast detection and accurate estimation.

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Fault Detection and Isolation for Deep Space Satellites

Cited by 38 publications

References 4 publications

Active fault‐tolerant attitude control for flexible spacecraft with loss of actuator effectiveness

Active fault‐tolerant attitude control for flexible spacecraft with loss of actuator effectiveness

Fault detection and isolation of satellite gyroscopes using relative positions in formation flying

A Multiple-Observer Scheme for Fault Detection, Isolation and Recovery of Satellite Thrusters

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